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Posttest report for the Advanced Solid Rocket Motor (ASRM) igniter discharge port flow testThe primary purpose of this test was to determine discharge coefficients for both the center axial and radial 2:1 aspect ratio exhaust ports of the ASRM multi-port igniter. In addition, both ports were tested with chamfered leading edge to assess how much improvement in discharge coefficient could potentially be achieved.
Document ID
19960002954
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Sringer, Anthony M. (NASA Marshall Space Flight Center Huntsville, AL, United States)
Date Acquired
September 6, 2013
Publication Date
July 28, 1993
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
NAS 1.15:110854
NASA-TM-110854
Report Number: NAS 1.15:110854
Report Number: NASA-TM-110854
Accession Number
96N12963
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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